CN105221192B - Cooling duct for gas turbine exhaust inner shell - Google Patents
Cooling duct for gas turbine exhaust inner shell Download PDFInfo
- Publication number
- CN105221192B CN105221192B CN201510319867.8A CN201510319867A CN105221192B CN 105221192 B CN105221192 B CN 105221192B CN 201510319867 A CN201510319867 A CN 201510319867A CN 105221192 B CN105221192 B CN 105221192B
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- Prior art keywords
- cooling channel
- inner shell
- pillar
- cooling
- parting line
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- 238000001816 cooling Methods 0.000 title claims abstract description 254
- 239000012809 cooling fluid Substances 0.000 claims abstract description 4
- 239000004744 fabric Substances 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims 2
- 239000007789 gas Substances 0.000 description 11
- 239000000567 combustion gas Substances 0.000 description 8
- 238000010438 heat treatment Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000000518 rheometry Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000037361 pathway Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003685 thermal hair damage Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The present invention discloses a kind of internal housing member for turbine, the internal housing member includes: ring-shaped inner part shell, the ring-shaped inner part shell includes cooling channel, wherein the outer surface of the wall of each access from cooling fluid source to the inner shell extends through the wall of the inner shell；And pillar, the pillar extends outwardly from the outer surface of the inner shell, wherein the cooling channel is arranged on the inner shell, so that it is equidistant that a pair of cooling channel, which is the cooling channel and the corresponding pillar on the opposite side of each pillar, and in each pair of cooling channel,.
Description
Technical field
The present invention relates generally to the coolings of the exhaust section of combustion gas turbine, and more particularly, in exhaust section
Combustion gas turbine inner shell on pillar cooling.
Background technique
Gas turbine engine combustion fuel and the mixture of compressed air are to generate hot combustion gas, the hot combustion gas
Turbine blade is driven to rotate the axis supported in exhaust section by bearing and cylinder.The rotation of axis can generate big calorimetric in the turbine
Amount.In addition, flowing through the heat turbine exhaust of exhaust section can transfer heat on the exhaust casing in exhaust section.
Inner shell in the exhaust section of combustion gas turbine is by the heating exhaust gas from turbogenerator.Due to coming from
The friction of cylinder axis, inner shell can also be subjected to thermal heat.Due to the difference of the main quality of entire inner shell, such as dividing
Difference at loft and on the flange at the pillar root for being connected to inner shell, the inner shell in gas turbine exhaust component
Body may be unable to fully and equably cool down.The inhomogeneous cooling of pillar may cause the thermal contraction of the different zones of inner shell
With the difference of thermal expansion, and cause damage associated with thermal stress.
It has been described using cooling fluid (for example, surrounding air) stream by exhaust section and cools down gas turbine exhaust cylinder portion
The method of part.Cooling system is in 7,493,769,6,578,363,7,373,773,2013/0064647 and of U.S. Patent number
It is disclosed in 2013/0084172.
Summary of the invention
This specification conceived and disclose it is a kind of for providing cooling stream in gas turbine exhaust section come in uniformly cooling down
The inner shell cooling system of the root of pillar and splitline flange on portion's shell, to solve more than in the presence of this field
Technical problem.
One embodiment of the application discloses a kind of internal housing member for turbine, the internal housing member
It include: ring-shaped inner part shell, the ring-shaped inner part shell includes cooling channel, wherein every access is extended through from cooling fluid source
Cross the inner shell wall reach the inner shell the wall outer surface；And pillar, the pillar is from described interior
The outer surface of portion's shell extends outwardly, wherein the cooling channel is arranged on the inner shell, so that a pair of of institute
It states cooling channel and is located at opposite side in each of the pillar, and the cooling channel of every centering is with corresponding pillar
Spacing.
The cooling channel may include in a pair of of cooling channel of the opposite side of die parting line, and the cooling channel is in axial side
The outer surface of the inner shell is extended up through, and is located at the pair of cooling of the opposite side of the die parting line
Access is equidistant with the die parting line.The cooling channel can be arranged in unequal spacing the circumference of the inner shell
Around.The cooling channel may include being arranged to circular array in the front and back of the pillar along the axis of the inner shell
The cooling channel of column.The cooling channel, which can be oriented to towards the pillar, guides cooling outflow across the access.
Another embodiment of the application discloses a kind of gas turbine exhaust section, and the gas turbine exhaust section includes: outside
Circulating line, the outer annular pipeline are configured to receive the exhaust from turbine, and including external shell outer cover and
Inner shell outer cover；Pillar, the pillar extend between the inner shell outer cover and the outer ring housing shells, wherein
The pillar extends through the outer annular pipeline；Inner annular pipeline, the inner annular pipeline are and the external rings
Shape pipeline is coaxial and is configured to receive cooling air, wherein cooling air is provided in described by the inner annular pipeline
Portion's housing shells, wherein the inner shell includes the outer wall with the cooling channel for the cooling air, and every
Cooling channel extends through the outer wall to allow cooling air to flow to the outer surface of the outer wall, and the cooling channel
It is arranged on the inner shell, so that a pair of cooling channel is located at opposite side in each of the pillar, and every
The cooling channel of centering is equidistant with corresponding pillar.
Detailed description of the invention
Fig. 1 is the front view with the conventional frontside of inner shell of cooling channel；
Fig. 2 is the front view with the conventional rear side of inner shell of cooling channel；
Fig. 3 is the exhaust of the combustion gas turbine with the inner shell including being evenly arranged in the cooling channel near pillar
The side view of section；
Fig. 4 is the front view of the front side of inner shell, shows the cooling channel arrangement near pillar；
Fig. 5 is the front view of the rear side of inner shell, shows the cooling channel arrangement near pillar；
Fig. 6 is the side view for showing cooling channel and die parting line cooling channel；
Fig. 7 is putting for the inner shell of the cooling channel on the either side with the die parting line for being evenly arranged in inner shell
Big figure；
Fig. 8 is the enlarged drawing with the inner shell of cooling channel and die parting line cooling channel；And
Fig. 9 is the perspective view with the inner shell of cooling hole and die parting line cooling hole arrangement.
Specific embodiment
Fig. 1 shows the normal internal shell 100 with the cooling channel along inner shell.Inner shell 100 includes semicircle
Cylindrical housing shells, i.e. upper interior portion housing shells 120 and lower interior portion housing shells 130.Housing shells are by dividing
Two upper flanges 122 are connect with two lower flanges 132 at loft 106 in die parting line 106 (such as between cylinder shell
Linear slit) at be coupled.
The upper interior portion housing shells 120 of the internally positioned shell 100 of pillar 102 and lower interior portion housing shells 130 it is outer
On circumference 108.Pillar 102 on upper interior portion housing shells 120 and lower interior portion housing shells 130 is symmetrical, and
And pillar 102 is usually equidistant to each other.
As used in conventional combustion turbine exhaust section, inner shell is positioned such that from combustion gas turbine
The exhaust stream of heating leaves exhaust section and flowing through the pillar on inner shell.Exhaust stream can flow through pillar in the X direction.
Cooling channel supply can be used for the cooling pillar heated by exhaust stream and by exhaust stream and by be attached to axis
Rotary heating inner shell cooling stream.
On the conventional frontside of inner shell 100, cooling channel 104 is usually equidistant to each other.Including cooling channel 104
It is connected to and extends between the inner periphery 110 of portion's shell 100 and the excircle 108 of inner shell 100.Cooling stream can be flowed from internal
The inner periphery 110 of shell 100 flows through cooling channel 104, and flows out excircle 108.Upper interior portion housing shells 120 have
Quantity is the cooling channel 104 of x, the cooling channel 104 from die parting line 106 along the circumference of inner shell 100 it is equal to each other between
Away from.It is the cooling channel 104 of x that lower interior portion housing shells 130, which have quantity,.Inner shell 100 in Fig. 1 have not with pillar
The cooling channel 104 that 102 layout is overlapped.Specifically, cooling channel 104 and being anisotropically located between pillar.
Similarly, Fig. 2 shows the rear sides of the inner shell 200 with cooling channel 204.The rear side of inner shell 200
Housing shells including semi-cylindrical, i.e. upper interior portion housing shells 220 and lower interior portion housing shells 230.Inner shell 200
Rear side include cooling channel 204, the cooling channel 204 extends and is connected between inner periphery 210 and excircle 208.
Cooling stream is to flow from inner periphery 210, flow through cooling channel 204 will cool down the rear side that stream is supplied to internally positioned shell 200
Pillar 202 on excircle 208.
The rear side of inner shell 200 has die parting line 206.At die parting line 206, by by two 222 Hes of upper flange
Two connections of lower flange 232 are to be coupled upper interior portion housing shells 220 and lower interior portion housing shells 230.Inner shell 200
Rear side have be located at upper interior portion housing shells 220 in 8 cooling channels 204 and be located at lower interior portion housing shells
8 cooling channels 204 in 230.The arrangement of cooling channel 204 is not also aligned with the layout of pillar 202.That is, cooling
Access 204 is simultaneously anisotropically located between pillar.
It has been found that the dislocation of pillar and cooling feed path cause to lead to each pillar of inner shell 100 and 200 with
The uneven distribution of the cooling stream of flange.The uneven distribution of cooling channel may cause high cooling rheology (high
Cooling flow variation) and non-uniform cooling to pillar and die parting line on inner shell.In routine
On portion's shell, pillar may be up to 60% to pillar rheology.Due to the lesser amount of cooling channel of each pillar, horizontal position
Pillar for example will usually meet with lower cooling flow rate.
In addition, the cooling stream around die parting line is usually to upset due to the construction of inner shell die parting line.Die parting line
Structure usually bigger than the other parts of cylinder shell, in the case where not placing die parting line around cooling channel, outside cylinder
The other parts of shell include upper flange and lower flange.Therefore, because cooling channel quantity is less, die parting line structure will be disturbed
The disorderly cooling stream around die parting line.
Due to lacking cooling channel in the zone, adequately cooling stream will not be received close to the pillar of die parting line.Phase
Than under, due to the greater number of cooling channel of each pillar in other regions of inner shell, other pillars will
With higher cooling flow rate.Due to insufficient cooling of inner shell, cooling channel divides relative to the uneven of layout of pillar
Cloth causes the reduction of the reliability of inner shell and pillar in gas turbine exhaust section.
The present invention provides a kind of cooling channel arrangements for increasing inner shell cooling uniformity.Cooling stream is uniformly distributed
It can help to reduce the out-of-roundness of exhaust frame, reduce the bearing landing for influencing rotor oscillation, and improve inner shell and branch
The reliability of column.
The combustion turbine exhaust section 390 with inner shell 300 is shown in Fig. 3.In operation, gas turbine starts
Machine room 380 will discharge the exhaust stream 382 of heating, and the exhaust stream 382 of the heating will flow through exhaust from turbogenerator room 380
Section 390.As exhaust stream 382 flows through exhaust pathway 396, exhaust stream 382 can encounter the pillar 302 on inner shell 300 simultaneously
Heat is transmitted to pillar 302 from exhaust stream 382.
In exhaust section 390, inner shell 300 may be coupled to rotatable shaft 350.Axis 350 can be to for sucking environment sky
Gas provides support as one group of propeller 392 of the cooling stream 394 for exhaust section 390.Cooling stream 394 can be to exhaust section 390
It is cooling to reduce the cause thermal damage as caused by heat that convection current is carried out with inner shell 300.
After cooling stream 394 is inhaled into inner shell 300, cooling stream 394 leaves inner shell from cooling channel 304
Body 300.The cooling inner shell 300 of 394 convection current of cooling stream including the cooling pillar 302 of convection current, and exhaust pathway is then added
Exhaust stream 382 in 396 is to leave exhaust section 390.
In Fig. 4, there are two housing shells, i.e. upper interior portion housing shells 420 and lower part for the front tool of inner shell 400
Inner shell outer cover 430.By by upper flange 422 and lower flange 432 connection come at die parting line 406 by upper interior portion shell
External cover 420 and lower interior portion housing shells 430 are coupled.
Upper interior portion housing shells 420 and lower interior portion housing shells 430 all have the excircle from inner shell 400
The 408 multiple pillars 402 stretched out.Inner shell 400, which is also included within, between inner periphery 410 and excircle 408 to be extended and is connected to
Cooling channel 404, the cooling channel 404 allow cooling stream across inner periphery 410 and excircle 408.
There is at least a pair of of cooling channel 404 in the either side in each of the pillar 402 on excircle 408.It is cooling logical
Road 404 need not along inner shell 400 excircle 408 it is equidistant to each other.However, cooling channel 404 will similarly with neighbour
Closely its each of pillar 402 is separated by a certain distance.For example, relative to exemplary strut 402A, exemplary cooling channel
404A and 404B is placed on the either side of pillar 402A.Between exemplary cooling channel 404A and 404B and exemplary strut 402A etc.
It is placed away from ground.
Similarly, in Fig. 5, the rear side of inner shell 500 has upper interior portion housing shells 520 and lower interior portion shell
Outer cover 530.By by upper flange 522 and lower flange 532 connection come at die parting line 506 by upper interior portion housing shells
520 and lower interior portion housing shells 530 be coupled.Upper interior portion housing shells 520 and lower interior portion housing shells 530 all have from
Multiple pillars 502 that the excircle 508 of inner shell 500 stretches out.
Inner shell 500 has cooling channel 504, and the cooling channel 504 is between inner periphery 510 and excircle 508
Extend and is connected to.There is at least a pair of of cooling channel 504 in the either side in each of the pillar 502 on excircle 508.
Cooling channel 504 need not be equidistant to each other along excircle 508, but cooling channel 504 will similarly with its neighbouring pillar
Each of 502 are separated by a certain distance.For example, cooling channel 504A and 504B are placed on pillar 502A relative to pillar 502A
Either side.Cooling stream feed path 504A and 504B and pillar 502A is equally spacedly placed.
In another embodiment, it is understood that there may be that stretches out from the excircle of inner shell is more than four pillars.In addition it counts
The pillar of amount can by the either side in each of multiple pillars with similar distance place the cooling channel of identical quantity come
It provides, such as figure 4 above and Fig. 5 are described and shown.
In a further embodiment, there may be more than a pair of of cooling channel on the either side in each of pillar.Branch
There may be more than two cooling channels or more than three cooling channels for the every side of column.Cooling channel will be symmetrically arranged at pillar
Either side, with the uniform cooling stream of each offer into pillar.
The distance between pillar and cooling channel are shown in Fig. 6, which provides the axis 650 being attached in combustion gas turbine
Inner shell 600 side view.Inner shell 600 has upper interior portion housing shells 620 and lower interior portion housing shells
630.By by upper flange 622 and lower flange 632 connection come at die parting line 606 by 620 He of upper interior portion housing shells
Lower interior portion housing shells 630 are coupled.The excircle 608 of inner shell 600 has multiple stretching pillars 602.
Inner shell 600 includes at least a pair of of cooling channel 604, this is arranged in along inner shell 600 cooling channel 604
The each pillar 602 of excircle 608 either side.Cooling channel 604 can be arranged so that each pair of cooling channel 604 and in outer circle
The center line S of pillar 602 on week 608 is at a distance of same distance M.
For example, exemplary strut 602A has the center line S extended from the mass centre of pillar towards second rim 670.Show
Example property cooling channel 604A and 604B is arranged in the either side of exemplary strut 602A along second rim 670, and exemplary cold
But every in access 604A and 604B and center line S are at a distance of same distance M.This arrangement by exemplary cooling channel 604A and
604B is equally spacedly placed on the either side of exemplary strut 602A.
Alternatively, there may be more than a pair of of cooling channel 604 on the either side of pillar 602.The of pillar 602
The quantity and pattern of the cooling channel 604 of side are logical relative to the cooling in second side that excircle 608 is placed on pillar 602
The quantity and pattern on road 604 are symmetrical.
Cooling channel 604 can along inner shell 600 the first wheel rim 660 and along 670 cloth of the second rim of inner shell 600
It sets.First group of cooling channel 604 is arranged to substantially with the first wheel rim 660 at a distance of same distance, and second group of cooling is logical
Road 604 is arranged to second rim 670 at a distance of similar distance.Alternatively, first group of cooling channel 604 can be along the first wheel rim
660 with pattern arrangement, and second group of cooling channel 604 can along with the symmetrical second rim of first group of access 604 670 with phase
As pattern arrange.
In another embodiment, other than the cooling channel 604 arranged adjacent to each pillar 602, in top
There is the die parting line cooling channel placed along die parting line 606 in 630 the two of portion's housing shells 620 and lower interior portion housing shells
614.Die parting line cooling channel 614 also extends between the inner periphery of inner shell 600 and the excircle 608 of inner shell 600
And it is connected to.The arrangement of cooling channel 604 and die parting line cooling channel 614 is further shown in Fig. 7.
Inner shell 700 amplifies in Fig. 7 to show the pillar 702 of die parting line 706 and neighbouring die parting line 706, also
The first wheel rim 760 and second rim 770 of inner shell 700.Inner shell 700 includes on upper interior portion housing shells 720
Upper flange 722 and the lower flange 732 on lower interior portion housing shells 730.Upper flange 722 and lower flange 732
It is coupled at die parting line 706 to form inner shell 700.
Upper flange 722 has thickness Q2 along excircle 708.Similarly, lower flange 732 has thickness along excircle 708
Spend R2.Die parting line cooling channel 714 is placed in close proximity to die parting line 706, adjacent upper portions flange 722 and lower flange 732.Divide mould
Line cooling channel 714 is positioned to the border distance Q1 with the upper flange 722 close to cooling channel 714.Similarly, divide mould
Line cooling channel 714 is positioned to the border distance R1 with the lower flange 732 close to cooling channel 714.If desired, away from
It may be the same or different from Q1 and R1.
However, if upper flange 722 is different with the thickness of lower flange 732, in upper interior portion housing shells 720
On lower interior portion housing shells 730, die parting line cooling channel 714 can not be with die parting line 706 at a distance of same distance.Die parting line is cold
But access 714 is positioned to facilitate the cooling of upper flange 722 and lower flange 732.
Different from die parting line cooling channel 714, cooling channel 704 is not placed relative to die parting line.Cooling channel 704 with
The distance of upper flange 722 may differ from a distance from lower flange 732, and may differ from a distance from die parting line 706.It is cold
But access 704 is placed according to the layout of pillar 702.
For example, on upper interior portion housing shells 720, cooling channel 704 can with 706 distance O of die parting line, and
On lower interior portion housing shells 730, cooling channel can be with 706 distance P of die parting line.If pillar is relative to excircle
708 equally spacedly place, then distance O and distance P can be identical, or if pillar is not equidistant relative to excircle 708
Ground is placed, then distance O and distance P can be different.
In addition, die parting line cooling channel 714 can be symmetrically disposed at outside upper interior portion housing shells 720 and lower interior portion shell
On cover 730.For example, on exemplary cooling hole 704A on upper interior portion housing shells 720 and lower interior portion housing shells 730
It is separated that exemplary cooling hole 704B passes through die parting line 706.Exemplary cooling hole 704A and exemplary cooling hole 704B are symmetrical
It places.Similarly, it is separated to pass through die parting line 706 by exemplary die parting line cooling hole 714A and exemplary cooling hole 714B.Show
Example property die parting line cooling hole 714A and exemplary die parting line cooling hole 714B is symmetrically positioned.
First group of cooling hole 704 and die parting line cooling hole 714 can be placed close to first round edge 760, and second group of cooling
Hole 704 and die parting line cooling hole 714 can be placed close to second rim 770.First group and second group is symmetrically positioned.
Alternatively, more than two die parting line cooling channels can adjacent upper portions flange and lower flange placement.A plurality of point of mould
Line cooling channel can be symmetrically placed on upper interior portion housing shells and lower interior portion housing shells, so that die parting line upper flange
It is uniformly cooled with die parting line lower flange.Die parting line cooling channel can equally spacedly be placed along upper flange and lower flange.
Fig. 8 shows two exemplary cooling channel 804A and 804B of neighbouring exemplary strut 802, the cooling channel
804A and 804B has the size that can be conducive to cool down the pillar that stream is supplied at die parting line and upper flange and lower flange
And orientation.As shown in Figure 4 and Figure 5, cooling channel extends between the inner periphery of inner shell and the excircle of inner shell.Cause
This, exemplary cooling channel 804A and 804B allows cooling stream 894 to pass through from the inner periphery of inner shell 800 to inner shell
800 excircle 808.
Exemplary cooling channel 804A and 804B is placed on the either side of pillar 802, and exemplary cooling channel
804A and 804B is directed towards the cooling stream 894 of the guidance of pillar 802.Exemplary cooling hole 804A is with the axis relative to cooling hole
Line Z angulation θ 1 is oriented, and exemplary cooling hole 804B is relative to axis Z angulation θ 2 to orient.
For example, angle θ 1 and angle θ 2 can adjacent struts 802 it is symmetrically placed.Exemplary cooling channel 804A and 804B is oriented to
So that cooling stream 894 passes through pillar 802 and is directed to the pillar 802.Cooling channel 804A and 804B can be relative to extending through
The axis Z at via hole center is at 15 degree, 30 degree, 45 degree, 60 degree, 75 degree, 90 degree, 105 degree, 120 degree, 135 degree, 150 degree or 165 degree
Angle.
In addition, cooling channel 804A and 804B can be in any kind of shape such as taper, cylinder, rectangle, spherical shape, hemisphere
Shape and their combination.
Exemplary cooling channel 804A and 804B can be placed such that the second rim 870 of they and inner shell 800 is
It at equal intervals, and also is equidistant with the pillar 802 on excircle 808.
Inner shell 800 can also also comprise die parting line cooling channel 814.Die parting line cooling channel 814 is oriented to court
To die parting line 806, and such as upper flange 822 of one in the flange on neighbouring die parting line 806 is placed.Die parting line cooling channel
814 can be in any kind of shape such as taper, cylinder, rectangle, spherical shape, hemispherical and their combination.
Die parting line cooling channel 814 can also be relative to axis Z at 15 degree, 30 degree, 45 degree, 60 degree, 75 degree, 90 degree, 105
Degree, 120 degree, 135 degree, 150 degree or 165 degree of angles.Preferably, die parting line cooling channel 814 is oriented such that across dividing mould
The cooling stream 894 of line cooling channel 814 is directed to die parting line 806.
Although Fig. 8, which is shown, can be used for cool down two cooling channels 804A and 804B that stream is supplied to exemplary strut 802,
But other cooling channels of other unshowned pillars of the Fig. 8 led on inner shell 800 can also be applied and be limited.Similarly,
Inner shell 800 may include other die parting line cooling channels 814 to supply more cooling streams to die parting line 806.
Advantages of the present invention includes the improvement cooling provided to inner shell, pillar and flange especially at die parting line
Root at, at the root, quality is different from the quality at other positions on inner shell.It has used in Fig. 9
The inner shell 900 shown analyzes the cooling of pillar 902.
Fig. 9 shows upper interior portion housing shells 920 and lower interior portion housing shells including being coupled at die parting line 906
930 inner shell 900.Upper interior portion housing shells 920 include 2 pillar S3 and S4 and upper flange 922.Cooling channel
904 are placed on the either side of pillar S3 and pillar S4, and 914 adjacent upper portions flange 922 of die parting line cooling channel is placed.
Similarly, lower interior portion housing shells 930 include 2 pillar S1 and S2 and lower flange 932.Cooling channel
904 are placed on the either side of pillar S1 and pillar S2, and die parting line cooling channel 914 is placed adjacent to lower flange 932.It is cooling
It flows from the inner periphery 910 of inner shell 900 across cooling channel 904 and die parting line cooling channel 914 and reaches inner shell 900
Excircle 908.Cooling stream is across cooling channel 904 guide stanchion S1, S2, S3 and S4, and cooling stream is across die parting line
914 guide rib 922 of cooling channel and flange 932.
Analysis has been made to determine the variation of the cooling stream for different types of inner shell: normal internal shell
Body, including invention cooling hole arrangement inner shell and including invention cooling hole and die parting line cooling hole arrangement in
Portion's shell.
It has been found that for normal inner shell such as Fig. 1 and inner shell shown in Figure 2 100 or inner shell 200,
The pillar that pillar on inner shell may meet with up to 60% cools down rheology to pillar.By by cooling channel equally spacedly
It is located in the either side of each pillar, pillar can be reduced to about 30% to the cooling rheologyization of pillar.For in addition to equally spacedly putting
It sets and is further comprised except the cooling channel of the either side of each pillar in the die parting line cooling channel that neighbouring die parting line is placed
Portion's shell, pillar can be reduced to about 15% to the cooling rheologyization of pillar.
Although describing the present invention in conjunction with most viable and preferred embodiment is currently regarded as, it is to be understood that the present invention is simultaneously
It is not limited to disclosed embodiment, on the contrary, the present invention is intended to cover including in the spirit and scope of appended claim
Various modifications and equivalent arrangements.
Claims (15)
1. a kind of internal housing member for turbine, the internal housing member include:
Ring-shaped inner part shell, the ring-shaped inner part shell includes cooling channel, wherein every access is extended through from cooling fluid source
Cross the inner shell wall reach the inner shell the wall outer surface；And
Multiple pillars, the multiple pillar extend outwardly from the outer surface of the inner shell, each the multiple branch
Column has mass centre；
Wherein the cooling channel is arranged on the inner shell, so that a pair of cooling channel is located at the multiple pillar
In each pillar opposite side, and the cooling channel of every centering and corresponding pillar be at equal intervals, it is each pair of described cold
But the distance between a cooling channel in access and the pillar are opposite mass centre's directions from the pillar
The distance that the center line S measurement that the inner shell extends obtains.
2. internal housing member as described in claim 1, wherein the cooling channel includes the opposite side positioned at die parting line
A pair of of cooling channel, the cooling channel extend through the outer surface of the inner shell, and position in the axial direction
In the pair of cooling channel of the opposite side of the die parting line be equidistant with the die parting line.
3. the internal housing member further comprises dividing mould such as claims 1 or 2 described in any item internal housing members
It is coupled at line to form the upper interior portion housing shells and lower interior portion housing shells of the inner shell.
4. internal housing member as claimed in claim 3, the internal housing member further comprises in the upper interior portion
Upper flange on housing shells and the lower flange on the lower interior portion housing shells, the upper flange and it is described under
Portion's flange is connected to form the die parting line.
5. such as the described in any item internal housing members of claims 1 or 2, wherein the cooling channel is not equally spacedly arranged
In the circumference of the inner shell.
6. such as the described in any item internal housing members of claims 1 or 2, wherein the cooling channel includes along the inner shell
The axis of body is arranged to the cooling channel of annular array in the front and back of the pillar.
7. such as the described in any item internal housing members of claims 1 or 2, wherein the cooling channel be directed towards it is described
Pillar cools down stream across the access to guide.
8. a kind of gas turbine exhaust section, the gas turbine exhaust section include:
Outer annular pipeline, the outer annular pipeline are configured to receive the exhaust from turbine, and including external shell
External cover and inner shell outer cover, the inner shell outer cover have upper interior portion housing shells and lower interior portion housing shells；
Multiple pillars, the pillar extend between the inner shell outer cover and the external shell outer cover, wherein described more
A pillar extends through the outer annular pipeline, and each the multiple pillar has mass centre；
Inner annular pipeline, the inner annular pipeline are coaxial with the outer annular pipeline and are configured to receive cooling
Air, wherein cooling air is provided to the inner shell outer cover by the inner annular pipeline,
Wherein the inner shell includes the outer wall with the cooling channel for the cooling air, and every cooling channel
The outer wall is extended through to allow cooling air flowing to the outer surface of the outer wall, and
The cooling channel is arranged on the inner shell, so that a pair of cooling channel is located at each of described pillar
Opposite side, and the cooling channel of every centering and corresponding pillar are at equal intervals one in each pair of cooling channel
The distance between a cooling channel and the pillar are opposite from the mass centre of the pillar towards the inner shell
The distance that the center line S measurement of extension obtains.
9. gas turbine exhaust section as claimed in claim 8, wherein the cooling channel includes the opposite side positioned at die parting line
A pair of of cooling channel, the cooling channel extend through the outer surface of the inner shell, and position in the axial direction
In the pair of cooling channel of the opposite side of the die parting line be equidistant with the die parting line.
10. gas turbine exhaust section as claimed in claim 9, wherein the cooling channel is arranged symmetrically around vertical axis.
11. such as the described in any item gas turbine exhaust sections of claim 9 or 10, wherein the cooling channel is directed towards institute
Die parting line is stated to guide cooling stream.
12. the gas turbine exhaust section further comprises in institute such as the described in any item gas turbine exhaust sections of claim 9 or 10
It states and is coupled at die parting line to form the upper interior portion housing shells and the lower interior portion housing shells of the inner shell.
13. gas turbine exhaust section as claimed in claim 12, the gas turbine exhaust section further comprises in the top
Upper flange on portion's housing shells and the lower flange on the lower interior portion housing shells, the upper flange and described
Lower flange is connected to form the die parting line.
14. such as the described in any item gas turbine exhaust sections of claim 8 to 10, wherein the cooling channel not equally spacedly cloth
Set the circumference in the inner shell.
15. such as the described in any item gas turbine exhaust sections of claim 8 to 10, wherein the cooling channel includes along the inside
The axis of shell is arranged to the cooling channel of annular array in the front and back of the pillar；Or wherein the cooling is logical
Road is directed towards the pillar to guide cooling stream across the access.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/301507 | 2014-06-11 | ||
| US14/301,507 US9903215B2 (en) | 2014-06-11 | 2014-06-11 | Cooling passages for inner casing of a turbine exhaust |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105221192A CN105221192A (en) | 2016-01-06 |
| CN105221192B true CN105221192B (en) | 2019-01-08 |
Family
ID=54706922
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510319867.8A Active CN105221192B (en) | 2014-06-11 | 2015-06-11 | Cooling duct for gas turbine exhaust inner shell |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9903215B2 (en) |
| JP (1) | JP6687335B2 (en) |
| CN (1) | CN105221192B (en) |
| CH (1) | CH709772A2 (en) |
| DE (1) | DE102015108908A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014105781A1 (en) * | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Frame strut cooling holes |
| US11566532B2 (en) * | 2020-12-04 | 2023-01-31 | Ge Avio S.R.L. | Turbine clearance control system |
Citations (6)
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|---|---|---|---|---|
| US20100080698A1 (en) * | 2008-09-30 | 2010-04-01 | General Electric Company | Method and apparatus for matching the thermal mass and stiffness of bolted split rings |
| US7785067B2 (en) * | 2006-11-30 | 2010-08-31 | General Electric Company | Method and system to facilitate cooling turbine engines |
| US20120006028A1 (en) * | 2010-07-08 | 2012-01-12 | Ching-Pang Lee | Damping resonator with impingement cooling |
| US20120186260A1 (en) * | 2011-01-25 | 2012-07-26 | General Electric Company | Transition piece impingement sleeve for a gas turbine |
| US20130084172A1 (en) * | 2011-10-03 | 2013-04-04 | General Electric Company | Turbine exhaust section structures with internal flow passages |
| US8727725B1 (en) * | 2009-01-22 | 2014-05-20 | Florida Turbine Technologies, Inc. | Turbine vane with leading edge fillet region cooling |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4410425B2 (en) | 2001-03-05 | 2010-02-03 | 三菱重工業株式会社 | Cooled gas turbine exhaust casing |
| JP4040556B2 (en) | 2003-09-04 | 2008-01-30 | 株式会社日立製作所 | Gas turbine equipment and cooling air supply method |
| US7004720B2 (en) * | 2003-12-17 | 2006-02-28 | Pratt & Whitney Canada Corp. | Cooled turbine vane platform |
| US7493769B2 (en) | 2005-10-25 | 2009-02-24 | General Electric Company | Assembly and method for cooling rear bearing and exhaust frame of gas turbine |
| JP5222384B2 (en) | 2011-09-09 | 2013-06-26 | 三菱重工業株式会社 | gas turbine |
-
2014
- 2014-06-11 US US14/301,507 patent/US9903215B2/en active Active
-
2015
- 2015-06-05 DE DE102015108908.4A patent/DE102015108908A1/en active Pending
- 2015-06-05 CH CH00810/15A patent/CH709772A2/en not_active Application Discontinuation
- 2015-06-08 JP JP2015115367A patent/JP6687335B2/en active Active
- 2015-06-11 CN CN201510319867.8A patent/CN105221192B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7785067B2 (en) * | 2006-11-30 | 2010-08-31 | General Electric Company | Method and system to facilitate cooling turbine engines |
| US20100080698A1 (en) * | 2008-09-30 | 2010-04-01 | General Electric Company | Method and apparatus for matching the thermal mass and stiffness of bolted split rings |
| US8727725B1 (en) * | 2009-01-22 | 2014-05-20 | Florida Turbine Technologies, Inc. | Turbine vane with leading edge fillet region cooling |
| US20120006028A1 (en) * | 2010-07-08 | 2012-01-12 | Ching-Pang Lee | Damping resonator with impingement cooling |
| US20120186260A1 (en) * | 2011-01-25 | 2012-07-26 | General Electric Company | Transition piece impingement sleeve for a gas turbine |
| US20130084172A1 (en) * | 2011-10-03 | 2013-04-04 | General Electric Company | Turbine exhaust section structures with internal flow passages |
Also Published As
| Publication number | Publication date |
|---|---|
| JP6687335B2 (en) | 2020-04-22 |
| CN105221192A (en) | 2016-01-06 |
| US20150361809A1 (en) | 2015-12-17 |
| US9903215B2 (en) | 2018-02-27 |
| JP2016006322A (en) | 2016-01-14 |
| CH709772A2 (en) | 2015-12-15 |
| DE102015108908A1 (en) | 2015-12-17 |
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